Missile wing bending and torsion angle measuring device and method

Abstract

The invention provides a missile wing bending and torsion angle measuring device and method. The method can be used for measuring the deformation angle of the missile wing on the ground under the no-load condition and can also be used for measuring the deformation angle of the missile wing under the loading condition. The device has the advantages of being simple in structure, convenient to install, adjustable in rigidity, high in stability and good in reliability, effectively solves the problem that the relative torsion angle of a missile wing is difficult to measure after the missile wing is assembled on a bomb, can meet the requirement that the device does not shake back and forth in the working process, guarantees the stability of a measurement system in the measurement process, and improves the measurement accuracy. According to the special structural form, structural parts of different sizes can be customized according to different aerial bomb weight grades and missile wing specifications and sizes.

Description

Technical Field

[0001] The invention relates to a device and method for measuring the bending and torsion angles of missile wings, which are applicable to the situations where the missile wings are loaded or unloaded, and are used for measuring the bending degree and torsion angle of the missile wing surface of gliding or loitering weapons, and belong to the technical field of precision-guided weapon measurement. Background Art

[0002] The high aspect ratio wing is the main lifting surface of the glide range extension and cruise weapons, providing most of the lift for the whole missile. The curvature and torsion angle of the wing surface of the high aspect ratio wing relative to the missile body are very important. The curvature is equivalent to forming a certain dihedral angle, which will cause asymmetry and imbalance in the aerodynamic shape. The torsion angle is equivalent to forming a certain angle of attack, which will cause changes in aerodynamic lift. Especially when the curvature and torsion angle of the wings on both sides differ greatly or even in opposite directions, it will have a greater negative impact on the flight control of the whole missile, resulting in the consumption of excessive rudder deflection angle for balance. In severe cases, it will cause the missile body control to diverge and cause the missile body to become unstable.

[0003] The surface of a large aspect ratio wing is a complex three-dimensional curved surface. Generally, a three-coordinate measuring machine or other means are used to measure the airfoil surface accuracy. It is often measured in the form of parts in the laboratory, which takes a long time to analyze and process, and this measurement method is not suitable for product-level measurement. Summary of the invention

[0004] The technical problem solved by the present invention is to overcome the deficiencies of the prior art and provide a method for measuring the bending and torsion angles of a wing, so as to conveniently and quickly calculate the bending and torsion angles of the wing.

[0005] The technical solution of the present invention is: a device for measuring the bending and torsion angles of a missile wing, the device comprising a base, a left wing surface bracket, a right wing surface bracket, an inclinometer, a laser displacement sensor array, a bus converter, a DC power supply, and a measurement computer;

[0006] A base is mounted on the projectile and is parallel to a reference plane of the projectile; the reference plane of the projectile is a plane tangent to the upper surface of the projectile and having a pitch angle of zero measured by an inertial measurement unit;

[0007] The left wing surface bracket and the right wing surface bracket are respectively installed on both sides of the base;

[0008] The laser displacement sensor array is installed on the left wing bracket and the right wing bracket to measure the distance between the wing bracket and the missile wing;

[0009] Inclinometer, used to measure the angle between the base and the projectile;

[0010] The power supply signal of the laser displacement sensor is connected to the DC power supply through the bus converter, and the collected data is connected to the measurement computer through the bus converter;

[0011] The measuring computer is used to calculate the bending and twisting angles of the missile wing according to the measurement results of each displacement sensor.

[0012] Preferably, the laser displacement sensor array comprises two types: a long-stroke laser displacement sensor array and a high-precision laser displacement sensor array; the long-stroke laser displacement sensor and the high-precision laser displacement sensor array are arranged in an alternating manner from the wing handle direction to the wing tip direction.

[0013] Preferably, the measuring stroke of the laser displacement sensor is not less than 300 mm.

[0014] Preferably, the measurement accuracy of the laser displacement sensor is better than 0.01 mm.

[0015] Preferably, the base is a flat plate structure with left and right wing bracket mounting interfaces, and the flatness at the interfaces is better than 0.02.

[0016] Preferably, the left wing surface bracket and the right wing surface bracket are grooved metal plate structures, have sensor installation interfaces, and the flatness at the interfaces is better than 0.02.

[0017] Preferably, the base is mounted on the surface of the elastic body by means of three leveling screws arranged in a herringbone shape, and the base surface is made parallel to the elastic body reference plane by adjusting the height of the leveling screws.

[0018] Another technical solution of the present invention is: a method for measuring the bending and torsion angles of a wing, the method comprising the following steps:

[0019] Position and install the left wing surface bracket and the right wing surface bracket on the base, and arrange the high-precision laser displacement sensor and the long-stroke laser displacement sensor on the wing surface bracket in sequence;

[0020] Use the base as the installation reference platform and place it on the upper surface of the projectile to be measured. Adjust the three leveling screws to keep the base parallel to the reference surface of the projectile.

[0021] The displacement difference of the test point corresponding to each sensor under no-load condition and under loaded condition is measured respectively;

[0022] According to the difference in displacement between the test point corresponding to each sensor under no-load conditions and under loaded conditions, the bending degree and torsion angle of the test point of the wing are calculated.

[0023] Preferably, the loading condition refers to: loading the wing vertically downward.

[0024] Preferably, an inclinometer is used to measure the angle between the base and the projectile in real time, and three leveling screws are adjusted to keep the base parallel to the reference plane of the projectile.

[0025] The beneficial effects of the present invention compared with the prior art are:

[0026] (1) The method for measuring the bending and torsion angles of a wing provided by the present invention can conveniently measure the distance between the wing surface and the parallel reference plane when the wing is deployed, thereby calculating the bending and torsion angles.

[0027] (2) The measurement method provided by the present invention is applicable not only to the basic angle measurement of the missile wing under no-load conditions, but also to the measurement of bending deformation, angle and torsion angle when a certain load (generally not greater than the load used during flight) is applied to the missile wing.

[0028] (3) The present invention arranges a long-stroke laser displacement sensor array and a high-precision laser displacement sensor array. Under large deformation, the long-stroke laser displacement sensor measurement results are used to calculate the bending and torsion angles of the missile wing. Under small deformation, the long-stroke laser displacement sensor measurement results are used to calculate the bending and torsion angles of the missile wing, taking into account the requirements of wide measurement range and high precision. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 This is a schematic diagram of the installation and use of an embodiment of the present invention;

[0030] Figure 2 This is a schematic diagram of the arrangement of a laser displacement sensor according to an embodiment of the present invention;

[0031] Figure 3 An enlarged view of the arrangement of the laser displacement sensor according to an embodiment of the present invention;

[0032] Figure 4 It is a front view of a body with a measuring device according to an embodiment of the present invention;

[0033] Figure 5 A side view of a body with a measuring device according to an embodiment of the present invention;

[0034] Figure 6 A top view of a body with a measuring device according to an embodiment of the present invention;

[0035] Figure 7 The figure is a flow chart of the use of the measuring device according to the embodiment of the present invention.

[0036] Figure 8 This is a schematic diagram of measuring points in an embodiment of the present invention;

[0037] In the figure,

[0038] 1-base; 2-leveling screw; 3-inclinometer; 4-screw; 5-right wing bracket; 6-high-precision laser displacement sensor; 7-long-stroke laser displacement sensor; 8-projectile. DETAILED DESCRIPTION

[0039] In order to make the present invention easier to understand, the present invention will be described in detail below with reference to embodiments and drawings. These embodiments and drawings are only for illustration and are not intended to limit the application scope of the present invention.

[0040] Figure 1 This is a schematic diagram of the installation and use of the present invention. Figure 2 This is a schematic diagram of the arrangement of the laser displacement sensor of the present invention. Figure 3 It is an enlarged view of the arrangement of the laser displacement sensor of the present invention.

[0041] The present invention provides a device for measuring the bending and torsion angles of a large aspect ratio missile wing, comprising a base, a left wing surface bracket, a right wing surface bracket, an inclinometer, a laser displacement sensor array, a bus converter, a DC power supply, and a measurement computer; the laser displacement sensor array comprises two types: a large-stroke laser displacement sensor array and a high-precision laser displacement sensor array; the large-stroke laser displacement sensor and the high-precision laser displacement sensor array are arranged in a staggered manner from the direction of the wing handle to the direction of the wing tip.

[0042] A base is mounted on the projectile and is parallel to a reference plane of the projectile; the reference plane of the projectile is a plane tangent to the upper surface of the projectile and having a pitch angle of zero measured by an inertial measurement unit;

[0043] The left wing surface bracket and the right wing surface bracket are respectively installed on both sides of the base;

[0044] The laser displacement sensor array is installed on the left wing bracket and the right wing bracket to measure the distance between the wing bracket and the missile wing;

[0045] Inclinometer, used to measure the angle between the base and the projectile;

[0046] The power supply signal of the laser displacement sensor is connected to the DC power supply through the bus converter, and the collected data is connected to the measurement computer through the bus converter;

[0047] The measuring computer is used to calculate the bending and twisting angles of the missile wing according to the measurement results of each displacement sensor.

[0048] The laser displacement sensor array includes two types: a long-stroke laser displacement sensor array and a high-precision laser displacement sensor array; the long-stroke laser displacement sensor and the high-precision laser displacement sensor array are arranged in a staggered manner from the wing handle direction to the wing tip direction. The measurement stroke of the laser displacement sensor is not less than 300mm. The measurement accuracy of the laser displacement sensor is better than 0.01mm.

[0049] Under large deformation, the long-stroke laser displacement sensor is used to measure the bending and torsion angles of the wing. Under small deformation, the long-stroke laser displacement sensor is used to measure the bending and torsion angles of the wing, taking into account the requirements of wide measurement range and high accuracy.

[0050] The base is a flat plate structure with left and right wing bracket mounting interfaces, and the flatness of the interfaces is better than 0.02. The left wing bracket and the right wing bracket are grooved metal plate structures with sensor mounting interfaces, and the flatness of the interfaces is better than 0.02.

[0051] The base is installed on the surface of the projectile through three leveling screws arranged in a herringbone shape. By adjusting the height of the leveling screws, an inclinometer is used to measure the angle between the base and the projectile to ensure that the base surface is parallel to the reference surface of the projectile.

[0052] The installation process of the device for measuring the bending and torsion angles of the above-mentioned high aspect ratio wing is as follows:

[0053] Using the base 1 as the installation reference platform, the base 1 can be placed on the upper part of the projectile 8 to be measured. By adjusting the three leveling screws 2, the base can be kept parallel to the projectile reference plane. The angle between the base and the horizontal plane can be measured by the inclinometer 3. Before arranging the base on the upper part of the projectile, the left wing bracket and the right wing bracket 5 need to be positioned and fixed on the base using screws 4, and high-precision laser displacement sensors 6 and long-stroke laser displacement sensors 7 are arranged on the wing brackets in sequence.

[0054] After installation, use the connecting cable to connect the bus converter, DC power supply and measurement computer. The laser displacement sensor communicates with the measurement computer through the serial port protocol, and the output data of the laser displacement sensor is displayed on the measurement computer.

[0055] Figure 4 This is a front view of the present invention with a measuring device, Figure 5 It is a side view of the present invention with a measuring device, Figure 6 It is a top view of the present invention with a measuring device, from Figures 4 to 6 It can be seen how the basic arrangement of the invention is used.

[0056] The present invention uses a high-rigidity left wing surface bracket and a right wing surface bracket as a measurement platform. The wing surface bracket has the same sweep angle as the missile wing and is equivalent to the size of the horizontal projection surface of the missile wing.

[0057] Figure 7 This is a flow chart for the use of the present invention. According to the sequence of the flow chart, the bending degree and torsion angle of the large aspect ratio wing under no-load condition can be measured.

[0058] The present invention also provides a method for measuring the bending and torsion angles of a large aspect ratio wing, the method comprising the following steps:

[0059] Position and install the left wing support and the right wing support on the base, and arrange the high-precision laser displacement sensor 6 and the long-stroke laser displacement sensor 7 on the wing support in sequence;

[0060] Use the base 1 as the installation reference platform and place it on the upper surface of the projectile 8 to be measured. By adjusting the three leveling screws 2, the base is kept parallel to the reference plane of the projectile. In this step, an inclinometer is used to measure the angle between the base and the projectile in real time, and the three leveling screws 2 are adjusted to keep the base parallel to the reference plane of the projectile.

[0061] The displacement difference of each sensor corresponding to the test point under no-load condition and under loaded condition is measured respectively; the loading condition refers to: loading the wing vertically downward;

[0062] According to the difference in displacement between the test point corresponding to each sensor under no-load conditions and under loaded conditions, the bending degree and torsion angle of the test point of the wing are calculated.

[0063] The measurement method in the specific embodiment of the present invention is as follows:

[0064] Fix the wing handle on the horizontal platform with the upper wing facing upwards, making sure the wing handle is level and stable without shaking. Figure 8 Among the P1-P5 and Q1-Q5 measuring points, Pi and Qi are a pair, located on a straight line parallel to the edge of the single wing. Figure 6 The measurement results of the ten measuring points P1-P5, Q1-Q5 are LP1-LP5, LQ1-LQ5, and the torsion angle of each section is calculated. The average torsion angle of the five sections P1Q1-P5Q5 can also be calculated. The torsion angle calculation method is:

[0065] δi=180*atan{[(LPi-LPRi)-(LQi-LQRi)] / DPQi} / 3.1416(°)

[0066] Where LPRi is the theoretical height of point Pi, LQRi is the theoretical height of point Qi, DPQi is the distance between the projections of Pi and Qi on the reference plane of the projectile, i = 1~5.

[0067] The same method can be used to calculate the torsion angle under loading conditions.

[0068] Considering that the theoretical height of the Pi point and the theoretical height of the Qi point are not easy to obtain, the displacement difference of the test point corresponding to each sensor under no-load conditions and loaded conditions can be compared, and the calculation method of the torsion angle of the test point can be calculated as:

[0069] δi'=180*atan{[(LPi-LPi')-(LQi-LQi')] / DPQi} / 3.1416(°)

[0070] DPQi is the distance between the projections of Pi and Qi on the reference plane of the projectile, i=1~5.

[0071] The calculation method of the bending degree of each measuring point is as follows:

[0072] Degree of curvature = (LPi-LPRi)-(LQi-LQRi);

[0073] The wing torsion angle is used to control the torsion angle of a pair of wings after assembly and are used in pairs.

[0074] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

Claims

1. A device for measuring the bending and torsion angles of a wing, characterized in that It includes a base, a left wing support, a right wing support, an inclinometer, a laser displacement sensor array, a bus converter, a DC power supply, and a measurement computer; A base is mounted on the projectile and is parallel to a reference plane of the projectile; the reference plane of the projectile is a plane tangent to the upper surface of the projectile and having a pitch angle of zero measured by an inertial measurement unit; The left wing surface bracket and the right wing surface bracket are respectively installed on both sides of the base; The laser displacement sensor array is installed on the left wing bracket and the right wing bracket to measure the distance between the wing bracket and the missile wing; Inclinometer, used to measure the angle between the base and the projectile; The power supply signal of the laser displacement sensor is connected to the DC power supply through the bus converter, and the collected data is connected to the measurement computer through the bus converter; The measuring computer is used to calculate the bending and twisting angles of the missile wing according to the measurement results of each displacement sensor.

2. A device for measuring the bending and torsion angles of a wing according to claim 2, characterized in that: The laser displacement sensor array includes two types: a long-stroke laser displacement sensor array and a high-precision laser displacement sensor array; the long-stroke laser displacement sensor and the high-precision laser displacement sensor array are arranged in a staggered manner from the wing handle direction to the wing tip direction.

3. A device for measuring the bending and torsion angles of a wing according to claim 2, characterized in that The measuring stroke of the laser displacement sensor is not less than 300 mm.

4. The device for measuring the bending and torsion angles of a wing according to claim 2, characterized in that: The measurement accuracy of the laser displacement sensor is better than 0.01 mm.

5. The device for measuring the bending and torsion angles of a wing according to claim 1, characterized in that: The base is a flat plate structure with left and right wing bracket mounting interfaces, and the flatness at the interfaces is better than 0.

02.

6. The device for measuring the bending and torsion angles of a wing according to claim 1, characterized in that: The left wing surface bracket and the right wing surface bracket are grooved metal plate structures, have sensor installation interfaces, and the flatness at the interfaces is better than 0.

02.

7. The device for measuring the bending and torsion angles of a wing according to claim 1, characterized in that: The base is mounted on the surface of the elastic body through three leveling screws arranged in a herringbone shape, and the base surface is made parallel to the reference surface of the elastic body by adjusting the height of the leveling screws.

8. A method for measuring the bending and torsion angles of a wing, characterized in that The steps include: Positioning and fixing the left wing surface bracket and the right wing surface bracket on the base, and sequentially arranging a high-precision laser displacement sensor (6) and a long-stroke laser displacement sensor (7) on the wing surface bracket; The base (1) is used as a mounting reference platform and is placed on the upper surface of the projectile (8) to be measured, and the three leveling screws (2) are adjusted to keep the base parallel to the reference surface of the projectile; The displacement difference of the test point corresponding to each sensor under no-load condition and under loaded condition is measured respectively; According to the difference in displacement between the test point corresponding to each sensor under no-load conditions and under loaded conditions, the bending degree and torsion angle of the test point of the wing are calculated.

9. A method for measuring the bending and torsion angles of a wing according to claim 8, characterized in that The loading condition refers to: loading the wing vertically downward.

10. A method for measuring the bending and torsion angles of a wing according to claim 8, characterized in that Use an inclinometer to measure the angle between the base and the projectile in real time, and adjust the three leveling screws (2) to keep the base parallel to the reference plane of the projectile.

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